Rotor/wing dual mode hub fairing system

ABSTRACT

A hub fairing system ( 12 ) for a stopped-rotor aircraft ( 10 ) having a fuselage ( 14 ) including a hub ( 16 ). The hub ( 16 ) is mechanically coupled to the fuselage ( 14 ) and to multiple blades ( 40 ) and is rotated by an engine ( 22 ). A retractable fairing ( 60, 64 ) covers a portion of the hub ( 16 ). An actuator ( 26 ) is coupled to the fairing ( 60, 64 ). A controller ( 28 ) is coupled to the actuator ( 26 ) and retracts the fairing ( 60, 64 ). A method of reducing drag on the aircraft includes transitioning between a rotary-wing mode and a fixed-wing mode. The fairing ( 60, 64 ) is deployed over a portion of the hub ( 16 ) upon the completion of the transition between flight modes.

GOVERNMENT CONTRACT

This invention was made with Government support under Contract NumberMDA 972-98-9-0009. The Government has certain rights in this invention.

TECHNICAL FIELD

The present invention relates generally to aeronautical vehicle dragreducing systems. More particularly, the present invention relates to asystem for minimizing parasitic drag associated with the hubs of astopped-rotor aircraft during its fixed-wing mode of flight.

BACKGROUND OF THE INVENTION

Helicopters are versatile aircraft in that they are capable of verticallift and forward propulsion without the need for a runway, unlike mostother passenger and cargo transporting style aircraft, such as propellerand jet powered aircraft. Unfortunately, helicopters are limited inforward speed.

In order to have vertical takeoff and landing capability of a helicopterand to have forward flight speed ability of other aircraft, differentstyles of vertical takeoff and landing (VTOL) aircraft are beingintroduced. One VTOL aircraft, in particular, is the canard rotor/wing(CRW) aircraft. A canard rotor/wing aircraft provides significantimprovements in forward speed over traditional style helicopters.Aircraft of the canard rotor/wing design, in general, include one ormore rotor/wings located on an aircraft fuselage that may be operated ina rotary-wing mode and in a fixed-wing mode. The rotor/wings include twosymmetrical blades and produce lift irrespective of flow direction.

There is a current desire to increase the drag efficiency of a canardrotor/wing aircraft. Improved drag efficiency results in less fuelneeded for a given mission, which in turn reduces the overall vehicleweight. Reduced vehicle weight can reduce vehicle-operating costs andallow for increased payload or cargo carrying capability of theaircraft.

As with traditional helicopters, approximately two-thirds of all draglinked with any canard/rotor wing aircraft can be traced to threefeatures, specifically the rotor, the rotor hub, and the interactionsthereof with the fuselage of the aircraft. Thus, there exists a need foran improved canard rotor/wing design with reduced drag associated withthe stated features.

SUMMARY OF THE INVENTION

The present invention provides a hub fairing system for an aircraft thathas a fuselage and rotor/wing. The hub fairing system includes a rotorhub that is mechanically coupled to the fuselage and to multiple blades.The hub and blades are rotated by an engine. A retractable fairingcovers a portion of the hub. An actuator is coupled to the fairing. Acontroller is coupled to the actuator and retracts the fairing.

A method of reducing drag on an aircraft of a canard rotor/wing designis also provided. The method includes transitioning between arotary-wing mode and a fixed-wing mode. This transitioning involvesstopping the rotation of a rotor/wing while supporting the weight of theaircraft via lift from the canard and tail of the aircraft. Uponcompletion of the transition, a fairing is deployed over the hub portionof the rotor/wing.

The embodiments of the present invention provide several advantages. Onesuch advantage is the provision of using one or more retractablefairings over a hub of a rotor/wing. The use of the fairings reducesdrag associated with the rotor/wing, hub, and fuselage of a canardrotor/wing aircraft and thus, improves aerodynamic performance of thataircraft. The reduced drag improves fuel economy and increasescargo-carrying capabilities of the aircraft.

Another advantage provided by an embodiment of the present invention isthe provision of one or more retractable hub fairings that areretractable within an outer mold line of a fuselage. When fullyretracted the hub fairings do not create drag normally associated withan open door, fairing, or access panel.

Yet another advantage provided by an embodiment of the present inventionis the provision of one or more fairings that, when deployed, form acontinuous aerodynamic surface with a fuselage and a rotor/wing. Thisfurther reduces drag of a canard rotor/wing aircraft when in afixed-wing mode.

The present invention improves functionality, performance,maintainability, and safety of a canard rotor/wing aircraft. Inaddition, the present invention is simplistic in design, reliable, andrelatively inexpensive to implement and to maintain.

The present invention itself, together with further objects andattendant advantages, will be best understood by reference to thefollowing detailed description, taken in conjunction with theaccompanying drawing.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a side view of a vertical takeoff and landing (VTOL) aircraftutilizing a single rotor/wing configuration and incorporating a dualmode rotor/wing hub fairing system in a deployed state in accordancewith an embodiment of the present invention.

FIG. 2 is a side view of the VTOL aircraft of FIG. 1 with the dual moderotor/wing hub fairing system in a retracted state in accordance with anembodiment of the present invention.

FIG. 3 is an isometric perspective and block diagrammatic view of a dualmode rotor/wing hub fairing system in accordance with an embodiment ofthe present invention.

FIG. 4 is a front close-up cutaway view of the portion of the dual moderotor/wing hub fairing system of FIG. 3.

FIG. 5 is a side view of the portion of the dual mode rotor/wing hubfairing system of FIG. 3.

FIG. 6 is a logic flow diagram illustrating a method of reducing drag onan aircraft in accordance with an embodiment of the present invention.

DETAILED DESCRIPTION

Unlike traditional helicopters that have continuously rotating bladeswhile in flight, a canard rotor/wing aircraft has one or more rotorsthat are not rotating during a significant portion of their flight. Thisfixed-wing mode allows for the use of a dual mode rotor/wing hub fairingsystem that is described in detail below.

In each of the following figures, the same reference numerals are usedto refer to the same components. A variety of other embodiments arecontemplated having different combinations of the below describedfeatures of the present invention, having features other than thosedescribed herein, or even lacking one or more of those features. Assuch, it is understood that the invention can be carried out in variousother suitable modes.

In the following description, various operating parameters andcomponents are described for one constructed embodiment. These specificparameters and components are included as examples and are not meant tobe limiting.

Referring now to FIGS. 1 and 2, side views of a vertical takeoff andlanding (VTOL) aircraft 10 utilizing a canard rotor/wing configurationand incorporating a dual mode rotor/wing hub fairing system 12 inaccordance with an embodiment of the present invention is shown.Although the present invention is primarily described with respect to arotor/wing aircraft of the canard design, the present invention may beapplied to other rotor/wing aircraft. For example, the present inventionmay be applied to a tandem rotor/wing aircraft.

The fairing system 12 is shown in a deployed state in FIG. 1 and in aretracted stated in FIG. 2. The aircraft 10 includes a fuselage 14, arotor/wing hub assembly 16 including a rotor/wing 18, a canard wing 20,and horizontal tail wings 21. The rotor/wing 18 is mechanically coupledto the fuselage 14 via the hub 16, which is rotated by one or moreengines 22. The pylori 23 couples the hub 16 to the fuselage 14. Thepylori 23 may or may not be used and may be referred to as an extensionand part of the fuselage 14. The fairing system 12, in general, includesthe fuselage 14, the hub 16, and the rotor/wing 18, as well as a hubfairing set 24 and an actuation system 25. The actuation systemdisplaces the fairing set 24 via one or more actuators 26. During flightthe fairing 24 is deployed to form a continuous aerodynamic hub surfaceswith the fuselage 14, or fuselage exterior body, and the rotor/wings 18.An example of a continuous hub surface 27, as stated, is shown in FIGS.1 and 5.

The rotor/wing 18 operates in dual modes including a rotary-wing modeand a fixed-wing mode. Thus, a rotor/wing aircraft refers to an aircraftthat has a wing or a set of blades that are capable of operating in botha rotary-wing mode and a fixed wing mode. In conjunction with theengines 22, the rotor/wing 18 enables takeoff, landing, low speed flightand hover capabilities of a helicopter and forward high speed liftcapabilities of a fixed-wing aircraft such as a jet transport. Inrotary-wing mode, the rotor/wing 18 functions as a helicopter rotor,propelling and providing lift for the aircraft 10. In fixed wing modethe rotor/wing 18 functions as a fixed wing, as on a traditionalairplane, and generates lift as a result of the aircraft's forwardvelocity. As the rotor/wing 18 is transitioned from the rotary-wing modeto the fixed-wing mode, the canard 20 and the tail wings 21 provide liftto the aircraft 10, thereby unloading the rotor/wing and allowing itsrotation to be stopped. A main controller 28 is coupled to therotor/wing 18 and switches between the rotary-wing mode and thefixed-wing mode. Although, the aircraft 10 is shown as having onerotor/wing 18, one canard 20, and two tail wings 21, additionalrotor/wings and fixed wings may be incorporated. The dynamic envelope 29of the rotor/wing 18 is shown.

The rotor/wing 18 includes at least two blades 40 that rotate to producelift in rotary-wing mode and are locked in a fixed position relative tothe fuselage in fixed-wing mode. To enable transition, engine power isgradually diverted from spinning the rotor to providing forward thrust.This diversion may be provided via a shaft drive (not shown), a reactiondrive 31, or via some other drive system known in the art.

The rotor/wing 18, canard 20, and the tail wings 21 may have a leadingor trailing edge devices, such as a flap, a slat, a flaperon, anaileron, a split aileron or other leading or trailing edge devices,known in the art, to provide control forces and moments during flight.

Although, the engines 22 are shown as being located in a forward portion31 of the aircraft 10, they may be located elsewhere on the aircraft 10.Each rotor/wing incorporated on the aircraft 10 may share a single setof engines or a separate set of engines may each be assigned to eachrotor/wing. The engines 22 may be turbofan engines or may be of someother type or style known in the art.

The controller 28 is preferably microprocessor based such as a computerhaving a central processing unit, memory (RAM and/or ROM), andassociated input and output buses. The main controller 28 may be aportion of a central vehicle main control unit, an interactive vehicledynamics module, a main safety controller, or be a stand-alonecontroller as shown.

Referring now to FIGS. 3-5, an isometric perspective and blockdiagrammatic view, a front close-up cutaway view, and a side view of therotor/wing portion 58 of a canard rotor/wing aircraft are shown. Thefairing system 12 includes the fairing sets 82, which each include anaft non-rotating fairing 60, a rotating fairing 62, and a forwardnon-rotating fairing 64. The aft non-rotating fairing 60 is located onan aft side 66 of the rotor/wing 18′ and the forward non-rotatingfairing 64 is located on a front side 68 of a rotor/wing 18′. Thenon-rotating fairings 60 and 64 are fixed to a fuselage 14′, thus theydo not rotate. The rotating fairing 62 is coupled directly to and overthe axis of rotation 70 of the rotor/wing 18′. The rotating fairing 62rotates with the rotor/wing 18′. When the rotor/wing 18′ is in astopped, the rotating fairing 62 does not rotate and is also fixed inposition. Of course, this is one possible fairing arrangement; otherarrangements and locations of fairing placements may be utilized.

The non-rotating fairings 60 and 64 pivot on hinges 72, which haveassociated hinge lines 74, between deployed and retracted positions. Thedeployed positions are represented by dashed lines 76. The hinges 72reside on or near the edge 78 of a fuselage exterior body panel 79nearest a hub fairing opening 80. The hinges 72 are attached away fromthe rotor/wing 18′ on the non-rotating fairings 60 and 64. Thenon-rotating fairings 60 and 64 have a center portion 82 and a pair ofouter flanges 84 coupled thereto. The center portion 82, when deployed,angles upward from the fuselage 14′ to the rotating fairing 62 withrespect to the plane 86 of the hub opening 80. The body panel edge 78,the hub fairing opening 80, and the plane 86 are best seen in FIG. 5.

The outer flanges 84 extend around an outer periphery 88 of the hub 16′away from the center portion 82. The outer flanges 84 may be integrallyformed with the center portion 82 as a single unit, as shown, or may beseparately attached components. The non-rotating portions 60 and 64include an upper edge line 90 and a lower edge line 92. The upper edgeline 90 follows or matches the contour of the corresponding mating areas94 on the rotor/wing 18′ and on the rotating fairing 62. The upper edgeline 90, in matching the contour of the rotor/wing 18′ and the rotatingfairing 62, provides an inherent brace therebetween. The lower edge line92 matches the contour of the fuselage 14′ near the hub opening 80.

The rotating fairing 62 extends over and cantilevers from the rotor/wing18′ on both sides 66 and 68 in a direction perpendicular to theextension of the blades 40′ of the rotor/wing 18′. In the embodimentshown, the rotating fairing 62 cantilevers beyond edges 66 and 68 infore and aft directions relative to the rotor/wing 18′ when in thefixed-wing mode. The rotating fairing 62 may be formed separate from therotor/wing 18′ and coupled thereto, as shown, or integrally formed aspart of the rotor/wing 18′.

The fairings 60, 62, and 64 may be of various types, styles, sizes, andshapes, and may be formed of various materials. The fairings 60, 62, and64 may be formed of a metal or composite commonly used in the aerospaceindustry, a honeycomb configured material, or other suitable materialknown in the art, or a combination thereof.

The non-rotating fairings 60 and 64 when deployed may be held inposition via the actuation system 25 or via one or more couplingelements (not shown). The coupling elements are used to attach the upperedge line 90 to the rotor/wing 18′ and/or to the rotating fairing 62.The coupling elements may include clips, magnetic locks, mechanical orelectrically actuated locking mechanisms, or other coupling elementsknown in the art. The coupling elements may also be coupled to thecontroller 28 for actuated control thereof.

The fairing system 12 may also incorporate guides (not shown) or otherdevices known in the art for maintaining alignment of the non-rotatingfairings 60 and 64.

The non-rotating fairings 60 and 64 are shown in both a deployedconfiguration, represented by dashed lines 98, and in a retractedconfiguration, represented by solid lines 99 in FIG. 4. The non-rotatingfairings 60 and 64 when retracted are stowed within an outer mold line100 of the fuselage 14′. The non-rotating fairings 60 and 64 pivot onthe hinges 72 and retract within the fuselage body or pylori 23′ abovethe fuselage structure or support frame 102. In being stowed within theouter mold line 100, the non-rotating fairings 60 and 64 do notintroduce any additional drag when retracted, such as an open door,fairing, or access panel might. The non-rotating fairings 60 and 64actually reduce drag even when retracted. This can best be seen in FIG.5. The shape of the non-rotating fairings 60 and 64 are such that whenretracted they extend around propulsion components, such as enginecomponents and plenum and exhaust ducting and components, and other hubassembly components. This is illustrated by the non-rotating fairings 60and 64 extending around the engines 22′ and engine ductwork 104, whichis also shown in FIG. 5.

The non-rotating fairings 60 and 64 are shown in both the deployedconfiguration, represented by outer solid lines 110 in FIG. 4, and inthe retracted configuration, represented by solid lines 112. The dynamicenvelope 114 of the rotor/wing 18′ is shown.

When the non-rotating fairings 60 and 64 are in the deployed state, thefairings 60, 62, and 64 and the pylori 23′ form the continuous flowsurface 27. Air flows over the fuselage 14′, over the center portions82, and over the rotor/wing 18′ across the rotating portion 62. Thissignificantly reduces drag commonly associated with the open hub area116.

The non-rotating fairings 60 and 64 when stowed do not fully retractbelow the hinge lines 74. This provides reduced drag when stowed. Thecenter portions 82, when retracted, remain in a partially uprightposition as to provide some fairing coverage over the hub area 116 andto allow air passage within a narrow area 118 between the rotor/wing 18′and the upper tips 120 of the non-rotating fairings 60 and 64. Air flowsover the fuselage 14′, over the center portions 82, and either over therotor/wing 18′ and rotating fairing 62 or through the narrow area 118when the non-rotating fairings 60 and 64 are in the retracted state.When retracted, the inner lower corners 120 of the non-rotating fairings60 and 64 may rest on and/or be held in place on the fuselage structure102.

In the retracted configuration and embodiment shown, the lower portion122 of the hub 16′ that resides at or below the swashplate 124 isshielded from outside air/turbulence by the non-rotating fairings 60 and64. The upper portion 126 of the hub 16′ that resides above theswashplate 124 and below the rotating fairing 62 is unshielded. When inthe deployed configuration, areas above, below, and at the swash platelevel of the hub 16′ are shielded by the non-rotating fairings 60 and64.

Environmental seals 130 may be disposed between the edges 90 and therotor/wing 18′ and the rotating fairing 62, on the edges 94, and on thefuselage 14′. The seals 130 may also be on the separation edges 132between the non-rotating fairings 60 and 64. The non-rotating fairings60 and 64 separate along the parting plane 134, which extends along andthrough the center of the rotor/wing 18′ when in the fixed-wing mode.The parting plane 134 extends vertically and laterally across thecorresponding aircraft and intersects the axis of rotation 70. The seals130 may be formed of various materials; a few examples are rubber,plastic, polyurethane, and polypropylene.

Referring now to FIG. 6, a logic flow diagram illustrating a method ofreducing drag on an aircraft in accordance with an embodiment of thepresent invention is shown.

In step 150, the aircraft 10 is operated in a rotary-wing mode togenerate vertical lift on a fuselage, such as the fuselage 14 or 14′.During the rotary-wing mode, the rotor/wing, such as the rotor/wing 18or 18′, is free to rotate similar to a helicopter. The exhaust gases areallowed to flow from the engines of the aircraft through the blades ofthe rotor/wings and exit the rotor/wing nozzles, such as the nozzles 44shown in FIG. 2, as to rotate the blades and thus the hubs, such as thehubs 16 or 16′. Rotation of the blades provides propelling and liftingmomentum.

In step 152, a controller, such as the main controller 28, switches theaircraft from operating in the rotary-wing mode to operating in afixed-wing mode. In step 152A, the controller begins off-loading lift ofthe rotor/wings, thus reducing rotational speed of the rotor/wings.Exhaust duct valves (not shown) are gradually closed to prevent exhaustgases from entering the blades and the exhaust gases are redirected toexit engine nozzles 23, to generate forward thrust. In step 152B, as thecontroller is off-loading lift of the rotor/wing, a canard wing and tailwings or some other transitional lift wing or combination thereof, suchas the canard 20 and the tail wings 21, provide the lift to maintainflight.

In step 152C, when the rotor/wing has come to a stop, the rotor/wing islaterally positioned relative to the fuselage. The gimbaling freedom ofthe rotor/wings is locked and any feathering hinges are locked out suchthat the rotor/wing does not have flapping degrees of freedom.

In step 152D, non-rotating fairings, such as the non-rotating fairings60 and 64, are deployed to cover a hub area between the fuselage and therotor/wings. The non-rotating fairings are pivoted upwards, such thattheir upper edges mate and seal with the rotor/wings and/or rotatingfairings, such as the rotating fairing 62. In step 152E, thenon-rotating fairings may be locked to the rotor/wing and/or to therotating fairing. In step 154, the aircraft is operated in thefixed-wing mode.

In step 156, the aircraft is switched from operating in the fixed-wingmode to the rotary-wing mode. In step 156A, the non-rotating fairingsare released or unlocked from the rotor/wing and the rotating fairing 62and retracted to below an outer mold line, such as the outer mold line100 of the fuselage. In step 156B, rotation of the rotor/wing isinitiated. Upon completion of step 156, the controller returns to step150.

The above-described steps are also meant to be illustrative examples;the steps may be performed sequentially, synchronously, simultaneously,or in a different order depending upon the application.

The present invention provides a dual mode canard rotor/wing hub fairingsystem that reduces drag on the aircraft during both a fixed-wing modeand a rotary-wing mode. The present invention reduces drag typicallyassociated with a rotor/wing, a hub, and a fuselage. The presentinvention encompasses the volume of space between the upper fuselage andthe rotor/wing of a canard rotor/wing aircraft with a smooth,aerodynamic shape that may be retracted out of the way of the dynamicenvelope swept out by the rotor/wing blades.

While the invention has been described in connection with one or moreembodiments, it is to be understood that the specific mechanisms andtechniques which have been described are merely illustrative of theprinciples of the invention, numerous modifications may be made to themethods and apparatus described without departing from the spirit andscope of the invention as defined by the appended claims.

1. A hub fairing system for an aircraft having a fuselage and a rotorthat is rotatable relative to the fuselage in a rotary-wing mode ofoperation and is fixed relative to the fuselage in a fixed-wing mode ofoperation, said hub fairing system comprising: a hub mechanicallycoupled to said rotor and rotatable relative to said fuselage and is ina vertically fixed position with respect to the fuselage; a firstfairing disposed forward of said hub that is movable between a deployedposition and a retracted position, said first fairing having an edgethat is disposed near to said rotor in said deployed position andfurther away from said rotor in said retracted position, and said firstfairing in said deployed position covering a portion of said hubdisposed between said rotor and said fuselage; a controller forcontrolling the position of said first fairing; and a first actuatormechanically coupled to said first fairing for moving said first fairingbetween said deployed and retracted positions in response to commandsignals from said controller.
 2. The system as recited in claim 1,wherein said first fairing has an external surface that forms acontinuous aerodynamic surface extending from said fuselage toward saidrotor in said deployed position of said first fairing.
 3. The system asrecited in claim 1, further comprising: a second fairing that is movablebetween a deployed position and a retracted position, said secondfairing having an edge that is disposed near said rotor in said deployedposition and further away from said rotor in said retracted position;and a second actuator mechanically coupled to said second fairing formoving said second fairing between said deployed and retracted positionsin response to command signals from said controller for controlling theposition of said second fairing.
 4. The system as recited in claim 3,and said second fairing is disposed aft of said hub.
 5. The system asrecited in claim 3, further comprising a fixed fairing that is fixed tosaid rotor, said first, second and fixed fairings forming adrag-reducing surface when said first and second fairings are in theirrespective deployed positions.
 6. The system as recited in claim 1,further comprising a fixed fairing that is fixed to said rotor, saidfirst and fixed fairings forming a drag-reducing surface when said firstfairing is in said deployed position.
 7. The system as recited in claim6, wherein portions of fixed second fairing extend in cantilever fashionforward and aft of said rotor respectively.
 8. The system as recited inclaim 6, further comprising an element for coupling said first fairingto said fixed fairing when said first fairing is in its deployedposition during said fixed-wing mode of operation.
 9. The system asrecited in claim 1, wherein said rotor comprises a plurality of blades.10. The system as recited in claim 1, wherein said first fairing in saidretracted position is stowed within an outer mold line of said fuselage.11. The system as recited in claim 1, further comprising a set ofhinges, said first fairing pivoting on said set of hinges duringmovement between its deployed and retracted positions.
 12. The system asrecited in claim 1, further comprising an element for coupling saidfirst fairing to said rotor when said first fairing is in its deployedposition during said fixed-wing mode of operation.
 13. The system asrecited in claim 12, wherein said coupling element is activated inresponse to a command signal from said controller.
 14. The system asrecited in claim 1, wherein said first fairing in said retractedposition extends around a propulsion component.
 15. The system asrecited in claim 1, wherein said first fairing in said retractedposition shields a portion of said hub lying below a swashplate fromoutside air turbulence.
 16. A hub fairing system for an aircraft havinga fuselage and a rotor that is rotatable relative to the fuselage in arotary-wing mode of operation and is fixed relative to the fuselage in afixed-wing mode of operation, said hub fairing system comprising: a hubmechanically coupled to said rotor and rotatable relative to saidfuselage and is in a vertically fixed position with respect to thefuselage; a first fairing that is movable between a deployed positionand a retracted position, said first fairing disposed forward of saidhub having an edge that is disposed near to said rotor in said deployedposition and further away from said rotor in said retracted position,and said first fairing in said deployed position covering a forwardportion of said hub disposed between said rotor and said fuselage; asecond fairing that is movable between a deployed position and aretracted position, said second fairing having an edge that is disposednear said rotor in said deployed position and further away from saidrotor in said retracted position, and said second fairing in saiddeployed position covering an aft portion of said hub disposed betweensaid rotor and said fuselage; a controller for controlling the positionsof said first and second fairings; a first actuator mechanically coupledto said first fairing for moving said first fairing between saiddeployed and retracted positions in response to first command signalsfrom said controller; and a second actuator mechanically coupled to saidsecond fairing for moving said second fairing between said deployed andretracted positions in response to second command signals from saidcontroller, wherein said controller is programmed to send said first andsecond command signals before the aircraft can be operated saidfixed-wing mode.
 17. The system as recited in claim 16, furthercomprising a third fairing that is fixed to said rotor, said first,second and third fairings forming a drag-reducing surface when saidfirst and second fairings are in their respective deployed positions.18. The system as recited in claim 17, wherein said first fairing has anexternal surface that forms a continuous aerodynamic surface extendingfrom said fuselage to said third fairing in said deployed position ofsaid first fairing, and said second fairing has an external surface thatforms a continuous aerodynamic surface extending from said fuselage tosaid third fairing in said deployed position of said second fairing. 19.The system as recited in claim 16, further comprising first and secondsets of hinges, said first fairing pivoting on said first set of hingesduring movement between its respective deployed and retracted positions,and said second fairing pivoting on said second set of hinges duringmovement between its respective deployed and retracted positions.